CN103158874B - For the substituted device of aircraft engine and for the method promoting the movement of aircraft - Google Patents
For the substituted device of aircraft engine and for the method promoting the movement of aircraft Download PDFInfo
- Publication number
- CN103158874B CN103158874B CN201210530460.6A CN201210530460A CN103158874B CN 103158874 B CN103158874 B CN 103158874B CN 201210530460 A CN201210530460 A CN 201210530460A CN 103158874 B CN103158874 B CN 103158874B
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- China
- Prior art keywords
- substituted device
- support
- cover
- hood
- electromotor
- Prior art date
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- 238000000034 method Methods 0.000 title claims abstract description 18
- 230000001737 promoting effect Effects 0.000 title claims description 8
- 230000001681 protective effect Effects 0.000 claims abstract description 20
- 230000005484 gravity Effects 0.000 claims description 6
- 230000008450 motivation Effects 0.000 description 4
- 238000012423 maintenance Methods 0.000 description 3
- 230000008878 coupling Effects 0.000 description 2
- 238000010168 coupling process Methods 0.000 description 2
- 238000005859 coupling reaction Methods 0.000 description 2
- 230000002349 favourable effect Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000012544 monitoring process Methods 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000000295 complement effect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000001141 propulsive effect Effects 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/50—Handling or transporting aircraft components
Landscapes
- Engineering & Computer Science (AREA)
- Transportation (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Manufacturing & Machinery (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Body Structure For Vehicles (AREA)
- Wind Motors (AREA)
Abstract
A kind of substituted device for replacing turbojet version aircraft engine; electromotor has and includes protective cover (21; 22) enging cabin (20) and there are two engine bearers (43; 44) support bar (42); each in described protective cover is installed into and pivots between an open position and a closed; described substituted device includes body (1), is attached to two anchor (2a of the engine bearer of motor support bar; 2b) and be suitable to receive the supporting part (23 belonging to protective cover; 24) support (11,12).A kind of method for this substituted device being arranged in enging cabin, the method makes it possible to close hood and permit the movement of aircraft.
Description
Technical field
The present invention relates to for aircraft engine, replacing especially for turbojet
For device.
These substituted devices are considered for assisting in flying device structure and the support work of maintenance
Tool.Under normal circumstances, this aircraft engine is typically attached to support bar and by enging cabin
Being protected, wherein, enging cabin includes the engine housing (protective cover) around electromotor.
Background technology
According to known prior art, (or multiple) electromotor sometimes must be removed with
The replacing safeguarding or being used for electromotor for described electromotor.But, in order to remove electromotor,
It is first necessary to open hood, hood is a part for enging cabin.In the prior art
It is known that when described hood is in an open position, aircraft cannot move, because flying
Row device moves and will cause the damage to hood or surrounding component.And, if working as electromotor not
In the presence of hood (this is normal position when the engine runs) in the closed position, fly
Row device cannot move equally, this is because owing to hood is maintained at suitable not over electromotor
When position, hood can damage each other.
It should be noted that in this article, hood (engine housing) can be referred to as " protecting
Guard shield " or it is simply referred as " cover ".
It is an object of the invention to provide one and solve prior art as above at least in part
The scheme of problem.
Summary of the invention
The present invention proposes the replacement as the turbojet version aircraft engine in propulsion system
The substituted device (that is, wig motivation) of thing, wherein, this propulsion system also includes enging cabin also
There is main shaft.
Described enging cabin includes at least one pair of protective cover for electromotor, and propulsion system
Including the motor support bar with at least two engine bearer；Each quilt in described protective cover
Being mounted to can be around the axis pivot between an open position and a closed being roughly parallel to main shaft
Turn.
Substituted device includes:
The body extended along first axle, this body is suitable to be roughly parallel to main shaft location,
Being fixed on the anchor of body, anchor is adapted for attachment to motor support bar
Engine bearer,
Support, protective cover can be placed on support.
Due to these devices, protective cover can be closed in substituted device and can be fastened on this
Position so that aircraft can be moved by its wheel, and does not damage the risk of hood.
One or more in following device can in the way of alone or in combination in the present invention not
Use with in embodiment.
According to an aspect, support can be arranged to generally curved；Therefore, cover can be put
Put on multiple positions of this arc.
According in terms of electromotor protective cover, the pair of protective cover is formed and is referred to as counter pushing away
Power apparatus cover have the first of First Series supporting part to cover, and enging cabin can include by
Be referred to as " fan guard " has the second of second series supporting part to cover；The support of substituted device
May include that the First Series support being suitable to receive the described supporting part of First Series supporting part,
And be suitable to receive the second series support of the described supporting part of second series supporting part.With this side
Formula, each in thrust reverser cover and fan guard can close and be fastened so that flight
Device can be moved.
According to a further aspect in the invention, the support of First Series support can be the most vertical
Directly it is arranged to generally curved in the first transverse plane of first axle, and second series supporting
The support in portion can be arranged to substantially in the second transverse plane being approximately perpendicular to first axle
Curved.Therefore, Mechanical Contact face between hood and substituted device thus be very similar to
Electromotor is in Mechanical Contact face when keeping in repair configuration between hood and electromotor.
According on the other hand, support can be regained at least in part.
According on the other hand, the support of second series support can be propped up by multiple collapsible arms
Support.In this way, the footprints of substituted device can be reduced, and does not particularly have when substituted device
When being arranged in propulsion assembly.
According on the other hand, this substituted device can also include hydraulic pressure unit and be suitable to fill replacement
Put the hydraulic cylinder being connected to every pair of cover.This makes it possible to the auxiliary lower-pilot electromotor in hydraulic system
Cover.
According on the other hand, this substituted device can also include wheel and pull bar.This substituted device
Therefore can be easily moved.
According on the other hand, this substituted device can also include promoting yoke portion.According to another aspect,
This yoke portion can be folding.In this way, this yoke portion can be folded, thus not with start
The closedown campaign interference of hood.
According on the other hand, this substituted device may be disposed so that the center of gravity position of this substituted device
In the center of gravity of its electromotor replaced in propulsion system or the immediate vicinity of electromotor.Cause
This, when substituted device is arranged in propulsion system, the weight balancing of wing and aircraft is similar to
General configuration when electromotor is arranged in propulsion system.
According on the other hand, this substituted device can also include inclinometer.Therefore, it can rising
When playing substituted device to be installed in propulsion system, the inclination of substituted device is monitored and
Control.
According on the other hand, this substituted device can also include being arranged on lifting yoke supporting part
Ergometer.Therefore, it can when promoting this substituted device to be installed in propulsion system this
Lifting device monitoring lifting force.
The method that the invention still further relates to movement for promoting aircraft, described Flight Vehicle Design becomes
Driven by least one turbogenerator propulsion system, wherein, at least one turbogenerator
Remove from propulsion system, and described propulsion system includes having at least two hood
Enging cabin, described at least two hood is pivotally mounted to allow when it is opened sending out
Motivation conducts interviews, and described hood is in its open position,
Said method comprising the steps of:
/ a/ installs and is attached substituted device to substitute turbogenerator, wherein, and this substituted device bag
Include: be adapted for attachment at least two anchor of the engine bearer of motor support bar；And
Support, hood can be placed on support,
/ c/ closes each hood,
/ d/ permits aircraft and moves.
Due to the method and this substituted device, hood can close in described substituted device
Close, and this aircraft can be moved by its wheel afterwards, and do not damage described electromotor
The risk of cover.
According to an aspect of the present invention, step/a/ can use interim installation capstan arrangement or
Lifting platform, enabling this substituted device is risen to alternative site.
According to an aspect of the present invention, this substituted device can include hydraulic cylinder, and therefore
The method is additionally may included in the following steps before step/c/, it may be assumed that
Hydraulic cylinder is attached to corresponding hood by/b/ so that can assist with the form of hydraulic pressure
Operation.
According to a further aspect in the invention, enging cabin can include being referred to as thrust reverser cover
First pair of hood and be referred to as second pair of hood of fan guard, and the method
Step/c/ includes following sub-step:
/ c1/ closes thrust reverser cover,
/ c2/ closes fan guard.Therefore each in thrust reverser cover and fan guard can be closed
Close and fasten to permit the movement of aircraft.
According to a further aspect in the invention, this substituted device can include hydraulic pressure unit and program list
Unit, and therefore can implement step/c1/ and/c2/ under the control of described program unit.With this side
Formula, can avoid potential maloperation.
Accompanying drawing explanation
By reading retouching of the following embodiment of the present invention to providing as non-limiting example
Stating, other aspects of the present invention, purpose and advantage will be apparent from.With reference to the accompanying drawings, also will be more preferably
Ground understands the present invention, wherein:
Fig. 1 diagrammatically illustrates the propulsion system for aircraft, and wherein, electromotor exists also
And hood opens；
Fig. 2 is the axonometric chart of substituted device according to the embodiment of the present invention；
Fig. 3 shows the propulsion system for aircraft in the case of not having electromotor, its
In, hood is opened, and substituted device is ready to install to substitute electromotor；
Fig. 4 is similar to Fig. 3, and Fig. 4 shows that same substituted device has been installed and sends out to substitute
Motivation；
Fig. 5 shows that substituted device has installed to substitute electromotor, wherein, and thrust reverser cover
Close；
Fig. 6 is similar to Fig. 4, and wherein, thrust reverser cover and fan guard are closed；
Fig. 7 shows the details in the region comprising the first support；
Fig. 8 shows the substituted device of Fig. 2 axonometric chart under travel position；And
Fig. 9 shows the details of the contact surface between supporting part and support.
Detailed description of the invention
When employing identical reference in various figures, they refer to identical or
Similar element.
Run through following whole description, by convention, term " front " and " afterwards " be about by
Thrust that the electromotor of aircraft is applied and for the aircraft direct of travel that causes；The direction
Corresponding to X plus sige (X+).
Fig. 1 diagrammatically illustrates the propulsion system 40 for aircraft.In shown example,
Described propulsion system 40 includes the turbine apparatus of turbojet h type engine h, this turbine apparatus under
Literary composition will be referred to collectively as " electromotor " 50.
Propulsion system 40 includes motor support bar 42, and this motor support bar 42 is by electromotor
50 wings 41 being connected to aircraft.In the configuration illustrated in this example, engine arrangement is at machine
Below the wing, and generally, electromotor is relative to wing biased forwards.It addition, motor support bar
42 include at least two engine bearer for electromotor 50 is fixed to motor support bar 42
43、44。
Propulsion system 40 also includes that enging cabin 20, enging cabin 20 include around electromotor 50
Parts.Especially, enging cabin includes aerodynamic fairing, and can support or
Including complementary engine accessory power rating.
Electromotor 50 and enging cabin 20 extend along main shaft X, and main shaft X generally and flies
The longitudinal axes coincident of device.
At least one pair of protective cover 21 that enging cabin 20 includes extending circumferentially over upon around electromotor 50,
22 (also referred to as hoods), this at least one pair of protective cover 21,22 is used in particular for protection and starts
Machine exempts to be affected by and also for improving the aerodynamic performance of propulsion system 40.
In example described herein as, enging cabin 20 includes two pairs of protective covers, i.e. be referred to as
The first of thrust reverser cover is to cover 21,22 and is referred to as the second of fan guard to cover 31,32.
Being mounted to can be around the first cover axis X 1 for first thrust reverser cover 21 (this is in left side)
Pivot, and the second thrust reverser cover 22 (this is in right side) being mounted to can be around the second cover axis
X2 pivots.
Cover axis X 1, X2 are preferably parallel to main shaft X and extend, but they can also be slight
Deviate from this parallel direction.
Being mounted to can be around flat with the first cover axis X 1 for first fan guard 31 (this is in left side)
Row or the axis overlapped pivot, and the second fan guard 32 (this is in right side) is with can be around with second
Cover axis X 2 axis that is parallel or that overlap pivotably is installed.
Fig. 1 illustrates hood 21,22,31,32 in an open position, wherein, this dozen
Open position be so that be capable of the internal part to electromotor and support member conduct interviews with
The position of the purpose including including maintenance, detection etc..
Normal in propulsion system 40 uses in position, and cover 21,22,31,32 is in closedown
Position, in this closed position, cover is generally circumferentially around engine arrangement；Enging cabin 20
Therefore have more or less for circle or slightly in avette outer cross section.
In shown example, each fan guard 31,32 be rendered as the most semicylindrical,
The thin flange being preferably made up of aluminium alloy.
In shown example, each cover 21,22 has the structure in the most semicylindrical thickness
Type.Thrust reverser cover includes the radial direction hollow inner part allowing a part for secondary gas flow to pass through
9 and radially outer parts 8, radially outer parts 8 include for making at least the one of secondary gas flow
It is partially toward the propulsive thrust mechanism of the anterior deflection of aircraft.
Will be described in more detail below each respectively including in cover 21,22,31,32 props up
Support part 23,24,33,34, supporting part 23,24,33,34 quilt when cover is in the closed position
It is supported on the specific region arranged for this purpose of electromotor and (shows the most in detail
Go out).
Locking breech lock 7 allows to each in cover is locked in closed position；In this way,
Closed position is fastened all normal operatings (including flight) when being used for aircraft.
Fig. 2 shows the substituted device 10 for substituting electromotor 50.This substituted device can be by
It is considered for assisting in flying device structure and the instrument of maintenance.It can also be referred to as, and " wig moves
Machine ".
Especially, substituted device 10 includes the body 1 extended along first axle A.This first axle
Line A can be substantially aligned with main shaft X, in order to substituted device 10 is arranged on propulsion system 40
In.In the illustrated example, body 1 has the form of beam, but it can have any other shape
Formula.
Substituted device 10 also includes at least two anchor 2a, the 2b being fixed on main body 1.This
The above-mentioned engine bearer 43,44 of a little anchor 2a, 2b motor support to be attached to bars,
Make it possible to be attached substituted device 10 to substitute electromotor.
Substituted device 10 also include being suitable to receiving above-mentioned belong to protective cover supporting part 23,24,33,
The support 11,12 of 34.
In this case, in shown example, the above-mentioned support 11 of substituted device 10,
12 include:
Be suitable to receive the supporting part of the First Series supporting part 23,24 belonging to thrust reverser cover
First Series support 11a, 11b, 11c, 11d, this First Series support in industry also
It is referred to as " V-shaped groove ",
Be suitable to receive the second of the supporting part of the second series supporting part 33,34 belonging to fan guard
Series support 12a, 12b, 12c, 12d.
Preferably, as shown in the figure, the support in First Series support 11 is the most vertical
Directly it is arranged to generally curved in the first transverse plane P1 of first axle A.Preferably,
A series of supports are arranged in the outer peripheral areas of plate 3.
Similarly, as it can be seen, the support of second series support 12 is being approximately perpendicular to
It is arranged to generally curved in the second transverse plane P2 of one axis A.Preferably, second series
Support is connected to front baffle 4.In this case, described front baffle 4 is set to be assembled into greatly
Cause to take in pentagonal mechanical welding.
It addition, shown substituted device 10 also includes wheel 15, in this example, four wheels
Son 15 is respectively mounted in fixing axle and steering spindle 6.
Advantageously, pull bar 16 can also be optionally secured to described steering spindle 6 so that substitutes dress
Put and can easily be moved and transport another position from a position.
According to optional feature, center of gravity G of described substituted device may be located at it in propulsion system
The center of gravity of middle replaced electromotor 50 or the immediate vicinity of electromotor 50.In this way, when
When substituted device 10 is installed in propulsion system, the weight balancing of wing and aircraft is similar to
General configuration when electromotor is arranged in propulsion system 40.
And, the weight of substituted device 10 will be chosen to this weight and be equal to substituted device
10 weight being designed to electromotor to be replaced.In this way, if an electromotor is substituted
Device is replaced, then left-right balance will not change.Such as, according to its to be replaced starting
The type of machine, the weight of substituted device can be between 2 tons to 5 tons.
According to optional feature, substituted device 10 can also include promoting yoke portion 14.In this example
In, it is proposed that using four to promote yoke portion, each yoke portion corresponds to a sling point, as by below
Describe in detail.When these yoke portions 14 can be such as folded up so that not with cover, especially
When being the closedown movement interference of thrust reverser cover 31,32, then it is favourable.
Specific device can be set so that the operation of substituted device 10 and movement.
Especially, in a favourable and optional feature, second series support 12
Support is supported by multiple collapsible arm 30a, 30b, 30c, 30d, 30e.The base portion of each arm
The chain connection on a section of pentagonal configuration 4 is welded with above-mentioned machinery.Each arm can be pivoted into
At a right angle with plane P2, enabling to be positioned at position approximately longitudinally.
Especially, such as Fig. 3, shown in 4 and 8, arm 30c, 30d, 30e that three downwardly extend
Can be folded when substituted device 10 rolls on the ground.
And, plate 3 can include being mounted to two that the axis around general vertical pivots collapsible
Sidepiece 3a, 3b.
Fig. 8 shows substituted device 10, and wherein, five collapsible arm 30a-30e are in folding
Position and two collapsible sidepiece 3a, 3b are in folding position.In this way, substituted device
The footprints of 10 is minimum, and this substituted device 10 can be transported by truck, and
Without departing from the standard size for highway transportation.
Substituted device 10 described herein also includes hydraulic pressure unit 27 and for by substituted device even
Receive hydraulic cylinder 28a, 28b, 29a, 29b of every pair of cover.
First hydraulic cylinder 28b makes it possible to be connected to substituted device 10 first thrust reverser cover
21.Second hydraulic cylinder 28a makes it possible to be connected to substituted device 10 second thrust reverser cover
22.The two hydraulic cylinder 28a, 28b are located close in the plane of plane P1.
3rd hydraulic cylinder 29b makes it possible to be connected to substituted device 10 first fan guard 31.The
Four hydraulic cylinder 29a make it possible to be connected to substituted device 10 second fan guard 32.
These connect hydraulic cylinder 28a, 28b, 29a, 29b has and is arranged on electromotor 50
The similar type of hydraulic cylinder and layout and can seeing the most in FIG.
Each hydraulic cylinder has: be attached to the end in the near-end of substituted device 10, such as Fig. 7
28b1；And be designed to attach to the far-end of facing cover, such as the end 28b2 in Fig. 7.
Hydraulic pressure unit 27 provides hydraulic coupling to these hydraulic cylinders under the control of a control unit 27.
This control unit can be to have button and the manual control unit of simple hardwired logic device, but
It can also include program unit, this program unit make it possible to operating process and with one or
Multiple pre-programmed compliances are tested.Thus possible faulty operation can be avoided.
Fig. 3 and Fig. 4 shows the operation installing substituted device 10 to substitute electromotor 50.Replace
For device 10 the most such as under the effect of tractor by pulling wheel to become and prop up with electromotor
Strut 42 aligns.
Interim " bootlace " formula hangar system 18 equipped with four erectings by overhang is installed.Each
Then the chain of erecting by overhang is attached to the above-mentioned lifting yoke portion 14 of substituted device 10.
After substituted device 10 is raised, anchor 2a, 2b are by starting with for being attached
Device that the device of machine is similar and be attached to engine bearer 43,44, as shown in Figure 4.
Once bearing 2a, 2b are locked in the appropriate position, then can remove interim hangar system
18。
It should be pointed out that, this interim hangar system 18 can be used for removing and replace reality
Electromotor 50.But, as the replacement to described hangar system, it is possible to use have for
Receive and promote abundant size and the lifting platform of power of substituted device 10.
After substituted device 10 is fixed on the bearing of motor support bar, by hydraulic cylinder
Each distal attachment in 28a, 28b, 29a, 29b is in the face of its corresponding cover.
Afterwards, can remove and when there is no electromotor or substituted device in propulsion system 40, keep cover
The specific bar that removably connects opened；Hereinafter these connecting rods will be retouched in more detail
State.
Then, thrust reverser cover 21,22 is moved to closed position, as shown in Figure 5.Can
With synchronization or nonsynchronous mode, hydraulic cylinder 28a, 28b are controlled；Equally, this can be with hands
Or controlled by auto-programming dynamicly.
Afterwards, fan guard 31,32 is moved to closed position, as shown in Figure 6.Can synchronize
Or hydraulic cylinder 29a, 29b are controlled by nonsynchronous mode；Equally, this can manually or
Controlled by auto-programming.
After four covers have been off, lower cover breech lock can be by already mentioned above and can
It is locked with the breech lock 7 seen in figure 6.
At this point it is possible to permit the movement of aircraft, without worrying thrust reverser cover and
The damage of fan guard.
Therefore, it can by following step relating to propulsion system and substituting dress as defined above
The method put is summarized, and wherein, this propulsion system does not have its turbogenerator and makes it
Motivation cover is opened, and this substituted device is for electromotor lacking in replacement, and described step is:
/ a/ install substituted device to substitute turbogenerator,
Hydraulic cylinder is attached to corresponding hood by/b/ (optional step),
/ c/ closes at least two hood,
/ d/ permits the movement of aircraft.
Preferably, the step closing cover performs with following two sub-steps:
/ c1/ closes thrust reverser cover 21,22,
/ c2/ closes fan guard 31,32.
Obviously, in order to remove substituted device 10 it to be replaced with electromotor, with contrary
Order performs the method, i.e. is first turned on fan and blinds, then opens thrust reverser cover.
Fig. 9 shows the principle of the contact surface between supporting part 23 and support 11a.Supporting part
The form of the fingers for being inserted in channel-shaped portion.When fingers 23 is in groove, prevent cover
All vertically move.The breech lock 7 that cover is locked in appropriate location makes it possible to firmly hold this
Position.
It is obvious also possible to use any other mechanical coupling system.
According to optional feature, substituted device 10 can also include inclinometer.Therefore, replacement is worked as
Device raised to be arranged in propulsion system time, the inclination of substituted device can be monitored and
Control.
According to optional feature, substituted device 10 can also include being arranged on lifting yoke supporting part
Ergometer.In this way, it is possible to substituted device raised to be arranged in propulsion system time pair
Substituted device monitoring lifting force.It should be pointed out that, according to optional characteristic, interim " bootlace "
Formula hangar system can also include ergometer.
It should be pointed out that, when electromotor or substituted device 10 are not located in it in propulsion system
Position in time, cover and stayed open by the specific removable bar that designs for this.First pair of bar
Thrust reverser cover 21,22 is connected to motor support bar 22.
Fan guard is connected to motor support bar 42 or is connected to already at opening by second pair of bar
The thrust reverser cover 21,22 of position.Described bar be arranged to not with by electromotor or substituted device
10 installations in moving system 40 are interfered.
The above-mentioned embodiment provided as non-limiting example is provided.The present invention is also
Relate within the scope of the claims and those skilled in the art it is contemplated that in the range of institute
There is embodiment variant.
Claims (12)
1. a substituted device (10), as the electromotor of the aircraft in propulsion system (40)
(50) substitute, described propulsion system (40) also includes enging cabin (20) and has master
Axis (X)；
Described enging cabin includes at least one pair of protective cover (21,22) for described electromotor,
And described propulsion system includes that the electromotor with at least two engine bearer (43,44) props up
Strut (42), each protective cover at least one pair of protective cover described is mounted to around being roughly parallel to
The axis (X1, X2) of described main shaft pivots between an open position and a closed,
Described substituted device (10) including:
-the body (1) that extends along first axle (A), described body (1) is suitable to almost parallel
Position in described main shaft (X)；
-at least two anchor (2a, 2b), described at least two anchor (2a, 2b)
It is fixed on described body and is adapted for attachment to the described at least two of described motor support bar and starts
Machine bearing (43,44)；
-support (11,12), at least one pair of protective cover described can be placed in described support (11,
12) on.
Substituted device the most according to claim 1, wherein, described support (11,12)
It is arranged to generally curved.
Substituted device the most according to any one of claim 1 to 2, wherein, described at least
A pair protective cover is formed be referred to as thrust reverser cover first to cover, and described first has the to cover
A series of supporting parts (23,24), and described enging cabin also include being referred to as fan guard (31,
32) second is to cover, and described second has second series supporting part (33,34) to cover,
And/or, the described support (11,12) of wherein said substituted device (10) includes being suitable to
Receive the First Series support of the described supporting part of described First Series supporting part (23,24)
(11a, 11b, 11c, 11d) and be suitable to receive described second series supporting part (33,34)
The second series support (12a, 12b, 12c, 12d) of described supporting part.
Substituted device the most according to claim 3, wherein, described First Series support
Support is arranged in the first transverse plane (P1) being approximately perpendicular to described first axle (A)
Become generally curved, and the support of wherein said second series support is being approximately perpendicular to
It is arranged to generally curved in stating second transverse plane (P2) of first axle.
Substituted device the most according to claim 1, wherein, described support is can be at least
Partly regain.
Substituted device the most according to claim 1, also includes hydraulic pressure unit (27) and is suitable to
Described substituted device is connected to the hydraulic cylinder (28) of at least one pair of protective cover described.
Substituted device the most according to claim 1, also includes wheel (15) and pull bar (16).
Substituted device the most according to claim 1, described substituted device is arranged so that described
The center of gravity (G) of substituted device is positioned at the institute that described substituted device is replaced in described propulsion system
State center of gravity or the immediate vicinity of described electromotor of electromotor.
Substituted device the most according to claim 1, also includes promoting yoke portion (14).
10., for the method promoting the movement of aircraft, described Flight Vehicle Design becomes by tool
At least one the turbogenerator propulsion system having enging cabin drives, wherein, and at least one whirlpool
Turbine removes from propulsion system, and described propulsion system includes enging cabin, described
Enging cabin has at least two hood, and described at least two hood is pacified pivotally
Dress, to allow when described at least two hood is opened, described electromotor to be conducted interviews,
Described at least two hood is in open position,
Wherein, said method comprising the steps of:
/ a/ installs and is attached substituted device (10) to substitute at least one turbogenerator described,
Described substituted device includes: be adapted for attachment to motor support bar (42) engine bearer (43,
44) at least two anchor (2a, 2b)；And support (11,12), described at least
Two hoods can be placed on described support (11,12),
/ c/ closes each hood,
/ d/ permits described aircraft and moves.
11. methods according to claim 10, wherein, described substituted device (10) includes
Towards the hydraulic cylinder (28a, 28b, 29a, 29b) of each hood, and described method is also
It is included in the following steps before step/c/:
Described hydraulic cylinder is attached to the corresponding described hood towards described hydraulic cylinder by/b/.
12. methods according to claim 10, wherein, described at least two hood is
It is referred to as first pair of hood of thrust reverser cover, and described enging cabin (20) also wraps
Include the second pair of hood being referred to as fan guard (31,32), and the step/c/ of described method
Including following sub-step:
/ c1/ closes described thrust reverser cover,
/ c2/ closes described fan guard (31,32).
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR1161302 | 2011-12-08 | ||
| FR1161302A FR2983836B1 (en) | 2011-12-08 | 2011-12-08 | TOOLS FOR AID FOR THE CONSTRUCTION AND MAINTENANCE OF AIRCRAFT |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103158874A CN103158874A (en) | 2013-06-19 |
| CN103158874B true CN103158874B (en) | 2016-08-24 |
Family
ID=47257704
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210530460.6A Expired - Fee Related CN103158874B (en) | 2011-12-08 | 2012-12-10 | For the substituted device of aircraft engine and for the method promoting the movement of aircraft |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US9915205B2 (en) |
| EP (1) | EP2602193B1 (en) |
| CN (1) | CN103158874B (en) |
| FR (1) | FR2983836B1 (en) |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2917710A1 (en) * | 2007-06-22 | 2008-12-26 | Aircelle Sa | FIXING PLATE AND LONGERON FOR HANDLING THE MONOBLOC PROPULSIVE ASSEMBLY OF AN AIRCRAFT |
| WO2014206380A1 (en) * | 2013-06-27 | 2014-12-31 | Hennlich S.R.O. | Mounting set for mounting and dismounting of aircraft engines |
| FR3014416B1 (en) | 2013-12-06 | 2015-11-27 | Microturbo | ADJUSTABLE SUSPENSION OF AN ENGINE TO POSITION IT IN RELATION TO ITS SUPPORT |
| FR3078058B1 (en) * | 2018-02-20 | 2022-03-25 | Safran Nacelles | MOTORIZATION ASSEMBLY FOR AIRCRAFT COMPRISING LIFTING POINTS, AND TROLLEYS FOR SUPPORTING SUCH AN ASSEMBLY |
| FR3085156B1 (en) * | 2018-08-24 | 2020-09-11 | Safran Nacelles | ASSEMBLY AND PROCEDURE FOR HANDLING AN AIRCRAFT PROPULSION ASSEMBLY |
| CN114728701A (en) | 2019-11-25 | 2022-07-08 | Mra系统有限责任公司 | Aircraft engine nacelle fairing mechanism |
| CN113716064A (en) * | 2021-08-17 | 2021-11-30 | 广州飞机维修工程有限公司 | Support tool for reverse thrust of aircraft engine and traction method for out-of-position engine |
| CN114313302B (en) * | 2021-12-23 | 2023-12-08 | 中国航空工业集团公司金城南京机电液压工程研究中心 | High-reliability aeroengine power housing opening actuation system and method |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4037809A (en) * | 1974-11-13 | 1977-07-26 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation | Device for mounting a turboreactor on an aeroplane |
| US5372338A (en) * | 1992-04-15 | 1994-12-13 | Rolls-Royce Plc | Mounting arrangement for a gas turbine engine |
| US6170141B1 (en) * | 1998-09-25 | 2001-01-09 | Stanley Aviation Corporation | Shipping system for jet aircraft engine and method of installing and removing jet aircraft engine |
| CN101105150A (en) * | 2006-07-13 | 2008-01-16 | 劳斯莱斯有限公司 | An engine core stand arrangement and method of removal and transportation of an engine core |
| US7959106B2 (en) * | 2006-09-20 | 2011-06-14 | Snecma | Integrated propulsive system comprising a bypass turbojet engine |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2685964A (en) * | 1954-08-10 | Engine contained with external | ||
| US4825648A (en) * | 1987-03-02 | 1989-05-02 | General Electric Company | Turbofan engine having a split cowl |
| FR2771710B1 (en) * | 1997-12-03 | 2000-02-11 | Aerospatiale | OPENING DEVICE COMMON TO TWO ADJACENT HOODS FOR AN AIRCRAFT NACELLE |
| US8720059B2 (en) * | 2010-04-29 | 2014-05-13 | Spirit Aerosystems, Inc. | Apparatus and method for aircraft engine core exchange |
-
2011
- 2011-12-08 FR FR1161302A patent/FR2983836B1/en not_active Expired - Fee Related
-
2012
- 2012-12-04 US US13/693,704 patent/US9915205B2/en not_active Expired - Fee Related
- 2012-12-04 EP EP12195549.6A patent/EP2602193B1/en not_active Not-in-force
- 2012-12-10 CN CN201210530460.6A patent/CN103158874B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4037809A (en) * | 1974-11-13 | 1977-07-26 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation | Device for mounting a turboreactor on an aeroplane |
| US5372338A (en) * | 1992-04-15 | 1994-12-13 | Rolls-Royce Plc | Mounting arrangement for a gas turbine engine |
| US6170141B1 (en) * | 1998-09-25 | 2001-01-09 | Stanley Aviation Corporation | Shipping system for jet aircraft engine and method of installing and removing jet aircraft engine |
| CN101105150A (en) * | 2006-07-13 | 2008-01-16 | 劳斯莱斯有限公司 | An engine core stand arrangement and method of removal and transportation of an engine core |
| US7959106B2 (en) * | 2006-09-20 | 2011-06-14 | Snecma | Integrated propulsive system comprising a bypass turbojet engine |
Also Published As
| Publication number | Publication date |
|---|---|
| FR2983836A1 (en) | 2013-06-14 |
| EP2602193B1 (en) | 2015-02-11 |
| FR2983836B1 (en) | 2014-12-19 |
| CN103158874A (en) | 2013-06-19 |
| EP2602193A1 (en) | 2013-06-12 |
| US20130145770A1 (en) | 2013-06-13 |
| US9915205B2 (en) | 2018-03-13 |
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Granted publication date: 20160824 Termination date: 20201210 |